X-wing helicopter-scout attack configuration

A single seat aircraft having an X-type wing which is rotatable for vertical takeoff and landing and capable of ceasing rotation during flight for increased forward speed and maneuverability, comprising:

• a main fuselage defining a longitudinal axis and including a single cockpit, and having engine air intakes and compressor intakes on opposing sides of said fuselage,
• a first and second fixed wings mounted on opposing sides of the fuselage,
• an X-type rotor-wing rotatably mounted to the top of the fuselage, said X-type rotor-wing having a plurality of rotor blades each having an axial passage extending along the length of the rotor and slots along leading and trailing edges of the rotor communicating with the respective axial passages for the controlled release of compressed air from said rotors in a sequential manner to control the maneuverability of the aircraft in flight,
• air compression drive means for receiving air from the air compressor intakes, compressing the air and distributing the compressed air to the axial passages of the X-type rotor-wing,
• first and second jet engines mounted vertically one above the other and aligned vertcially with respect to said longitudinal axis, said first and second engines respectively receiving air from the engine air intakes of the fuselage and directing first and second jet exhaust streams towards an aft end of the aircraft,
• first and second rotary power shafts, respectively coupled to said first and second jet engines, selectively receiving and communicating rotary torque therefrom,
• a common gear box connected to the first and second rotary power shafts for communicating rotary torque from the first and second rotary power shafts to the X-type rotor-wing and for further communicating rotary torque from the first and second rotary power shafts to the air compression drive means,
• an exhaust nozzle mounted in the extreme aft end of the fuselage perpendicular to the longitudinal axis of the fuselage;
• first and second pitch vectoring flap pairs, respectively rotatably mounted in the exhaust nozzle and rotating about an axis perpendicular to the longitudinal axis of the aircraft to respectively direct jet exhaust from the first and second jet engines in a generally vertical arc and control the pitch orientation of the aircraft in powered flight, said first pitch vectoring flap pair further being generally positioned within the exhaust nozzle to intersect a relatively dense core of jet exhaust from the first jet engine and said second pitch vectoring flap pair further being generally positioned within the exhaust nozzle to intersect a relatively dense core of jet exhaust from the second jet engine;
• and
• first and second yaw thrust vectoring flap cascades respectively mounted rotatably in opposing generally vertical sides of an aft portion of the fuselage and equally proximate the jet stream of the respective engine for respectively directing jet exhaust from the respective first and second jet engines in a generally horizontal arc and control the yaw orientation of the aircraft in powered flight,
• said first and second jet engines respectively provide rotary torque through the first and second rotary power shafts and gear box to rotate the X-type rotor-wing and provide aircraft vertical takeoff and landing and further respectively direct relatively dense cores of jet exhaust through the first and second pitch vectoring flap pairs and first and second yaw thrust vectoring flap cascades to control the pitch orientation of the aircraft and yaw orientation of the aircraft in powered flight.